Collisional balance of the meteoritic complex
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Keywords:
Hypervelocity
Zodiacal light
Micrometeoroid
Interplanetary medium
Radiation Pressure
Mass distribution
A single microparticle launching method is described to simulate the hypervelocity impacts of micrometeoroids and microdebris on space structures at the Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency. A microparticle placed in a sabot with slits is accelerated using a rifled two-stage light-gas gun. The centrifugal force provided by the rifling in the launch tube separates the sabot. The sabot-separation distance and the impact-point deviation are strongly affected by the combination of the sabot diameter and the bore diameter, and by the projectile diameter. Using this method, spherical projectiles of 1.0-0.1 mm diameter were launched at up to 7 km/s.
Hypervelocity
Micrometeoroid
Light-gas gun
Microparticle
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Increased sophistication in both, direct impact detectors and zodiacal light measurements encourages to discuss the compatibility of the results obtained by these quite different methods of investigating interplanetary dust. Taking recent measurements of particle fluxes and velocities obtained by the space missions of Pioneer 8/9 (Berg and Grün 1973), Heos 2 (Hoffmann et al. 1975), and comparing them with submicron-sized craters on lunar surface samples (Schneider et al. 1973, Fechtig et al. 1974) there seem to be two types of interplanetary dust populations: larger (>10 −12 g) micrometeorites orbiting around the sun as the classical zodiacal dust cloud and a second component of very small (<10 −12 g) particles coming radially from the direction of the sun with high velocities (>50 km/s). On the basis of the flux data referred to above and adopting for both components velocities of 10 or 50 km/s relative to the detector, respectively, a differential distribution function n(a) · da was found for the particle radii (a) as shown at a logarithmic scale in fig. 1. A density of 3 g/cm 3 was adopted in order to convert particle masses into radii. The regions A, B, C (see Table 1) correspond approximately to the regimes of “submicron particles”, the classical zodiacal cloud particles, and the meteoritic component of the interplanetary dust complex. From this information the brightness I(ε) of the zodiacal light in the ecliptic plane can be computed as a function of elongation by approximating the distribution function n(a) in the different regions by simple power laws a −k ·da and by adopting a resonable scattering function σ(θ) for the average scattering behaviour of one particle of the mixture depending on the scattering angle θ. By use of an inverse (v = 1) decrease of particle number densities n = n o · r −v with solar distance r(AU), where n o is the number density at r=1 AU, one obtains with a particle size distribution law n(a)da ~ a −k da in the different intervals of sizes (Table 1) the intensity of the zodiacal light (in stars of 10th magnitude per square degree, S 10 ) as shown in fig. 2. The two models (Maximum, Minimum) correspond to an upper and to a lower limit of particle number densities compatible with the in situ measurements, respectively.
Zodiacal light
Micrometeoroid
Interplanetary medium
Ecliptic
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This paper describes the design, construction, and testing of a hypervelocity impact (HVI) detection system for monitoring the occurrence of an impact, the location of the impact, and the resulting damage to a spacecraft. One of the constant dangers emanating from the space environment is the presence of micrometeoroids and space debris. The energy associated with these hypervelocity impacts is sufficient to penetrate most spacecraft structures, damage spacecraft components, and pose a potential threat to human occupants. A detection system has been developed involving optical fibers woven in an orthogonal grid in a fabric such as Kevlar. The optical fibers are interrogated by a light source that monitors the intensity of the light transmission. Changes in light transmission relate to HVI damage to the optical fibers such that a damage zone can be constructed based on these data. This “smart fabric” can be bonded to critical parts of the spacecraft susceptible to HVI damage or mounted inside the spacecraft structure such that the HVI particles are attenuated before they can damage interior components (and astronauts). Tests on a Kevlar smart fabric have been conducted at the National Aeronautics and Space Administration (NASA) Johnson Space Center using aluminum plate targets, and results are presented demonstrating the effectiveness of this technique.
Hypervelocity
Micrometeoroid
Space Suit
Kevlar
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Micrometeoroid
Hypervelocity
Solar energetic particles
Geocentric orbit
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Realizing and understanding the effects of the near-Earth space environment on a spacecraft during its mission lifetime is becoming more important with the regeneration of America's space program. Included among these potential effects are the following: erosion and surface degradation due to atomic oxygen impingement; ultraviolet exposure embrittlement; and delamination, pitting, cratering, and ring formation due to micrometeoroid and debris impacts. These effects may occur synergistically and may alter the spacecraft materials enough to modify the resultant crater, star crack, and/or perforation. This study concentrates on modelling the effects of micrometeoroid and debris hypervelocity impacts into aluminum materials (6061-T6). Space debris exists in all sizes, and has the possibility of growing into a potentially catastrophic problem, particularly since self-collisions between particles can rapidly escalate the number of small impactors. We have examined the morphologies of the Long Duration Exposure Facility (LDEF) impact craters and the relationship between the observed impact damage on LDEF versus the existing models for both the natural (micrometeoroid) and manmade (debris) environments in order to better define these environments.
Micrometeoroid
Hypervelocity
Overheating (electricity)
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Micrometeoroid
Hypervelocity
Regolith
Habitability
Lunar soil
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Abstract The effect of hypervelocity impacts from micrometeoroids and orbital debris (MOD) on spacecraft materials and structures is discussed in terms of observed flight damage and laboratory simulation tests. Methods of estimating the probability of impact as a function of particle size are presented based on particle distributions and orbital altitude. Two types of damage mechanisms are described: initial impact cratering, and debris plumes emanating from the impact site. Shielding systems currently employed are also described. With the return of human exploration of the moon, the effect of meteoroid impacts on lunar structures and equipment is also examined.
Micrometeoroid
Hypervelocity
Atmospheric entry
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Dust-sized olivine particles were fired at a copper plate using the Space Power Institute hypervelocity facility, simulating micrometeoroid damage from natural debris to spacecraft in low-Earth orbit (LEO). Techniques were developed for measuring crater volume, particle volume, and particle velocity, with the particle velocities ranging from 5.6 to 8.7 km/s. A roughly linear correlation was found between crater volume and particle energy which suggested that micrometeoroids follow standard hypervelocity relationships. The residual debris analysis showed that for olivine impacts of up to 8.7 km/s, particle residue is found in the crater. By using the Space Power Institute hypervelocity facility, micrometeoroid damage to satellites can be accurately modeled.
Hypervelocity
Micrometeoroid
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We investigated the effect of hypervelocity impacts of micrometeoroids and small-scale orbital space debris (M/OD) on space structures by comparing numerical simulation results obtained using the AUTODYN-2D hydrocode with the results of experiments using a two- stage light gas gun. The response of an aluminum honeycomb structure to 6 km/s high-velocity impacts is shown and discussed. AUTODYN-2D, which is used for impact analysis of complex physical systems including fluid and solid materials, was used to simulate impacts at 2–15 km/s. Material models used in the simulation to allow investigation of phenomena over a wide range of impact velocities, including shock-induced vaporization, are also presented and discussed.
Hypervelocity
Micrometeoroid
Light-gas gun
Vaporization
Honeycomb
Honeycomb structure
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Micrometeoroid
Zodiacal light
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Citations (1)